Guidance Summary and Assessment of the Chang’e-3 Powered Descent and Landing

Li, Shuang; Jiang, Xiuqiang; Tao, Ting

doi:10.2514/1.a33208

Cited by 55 publications

(33 citation statements)

References 10 publications

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“…Secondly, the testing of the created innovative technology on the spot was no less important for the Chinese space industry. After all, no one before among the space powers has sent missions to the other side of the Moon: "Similar to Chang'E-3 (CE-3), three types of sensors were employed by CE-4, including a laser ranging sensor, a microwave ranging and velocimeter sensor, and an optical imaging sensor, and a laser imaging sensor" (Li Shuang et al, 2016).…”

Section: From Space Exploration To Global Technological Leadershipmentioning

confidence: 99%

Untitled

2020

P&C

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The paper considers the philosophical, historical, practical, and futurological aspects of the whole complex of relationships between human and humanity with the Moon from being an object of cognition, exploration, usage, and development to total colonization in the paradigm of the global future and expansion into outer space. A "comprehensive" definition of the concept of "Moon exploration" is given. The article provides periodization and a brief description of the history and prospects of the exploration of the Moon in the context of evolution of goals, concepts, projects, and technologies. The concept of total exploration and colonization of the Moon is developed, which includes: a general model of the exploration process; a general super global project covering many individual projects; environmentally friendly technologies and projects (their general classification and examples). The main conclusions are formulated.

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Section: From Space Exploration To Global Technological Leadershipmentioning

confidence: 99%

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2020

P&C

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“…The comprehensive performance of the proposed CO-based guidance approach is tested in this case by implementing 1000-run Monte Carlo simulations. In the past missions, the distance between the initial target site and the final target site is usually no more than 50 m during planetary powered descent [5][6][7]. Just like the CE-3 lunar landing mission [6] flight scope near the surface of a spherical central planet, and the J 2 perturbing force and the irregular gravity change are very small and usually ignored [2].…”

Section: Case IImentioning

confidence: 99%

“…In the past missions, the distance between the initial target site and the final target site is usually no more than 50 m during planetary powered descent [5][6][7]. Just like the CE-3 lunar landing mission [6] flight scope near the surface of a spherical central planet, and the J 2 perturbing force and the irregular gravity change are very small and usually ignored [2]. The aerodynamic perturbing force and thrust deviation would be the main perturbations [2,4].…”

Section: Case IImentioning

confidence: 99%

“…After the 2012 Mars Science Laboratory (MSL) and the 2013 Chang'e-3 (CE-3) lunar lander missions, planetary powered descent guidance technologies have been further improved. More attention has been paid to the fuel optimality, robustness against uncertainty, and autonomous retargeting to avoid hazards [5,6]. An improved Apollo suboptimal-fuel guidance and some supplementary linear guidance laws were piecewise employed during MSL powered descent to ensure safe landing under uncertainty.…”

Section: Introductionmentioning

confidence: 99%

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Computational guidance for planetary powered descent using collaborative optimization

Jiang

Tao³

2018

Aerospace Science and Technology

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An innovative computational guidance framework is proposed for planetary powered descent using collaborative optimization approach. First, the dynamical model and constraints for planetary powered descent are presented. Then, using collaborative optimization strategy, the computational guidance framework for powered descent is formulated as a multi-discipline optimization problem including trajectory optimization, optimal guidance, and system-level optimization. Finally, the computational guidance approach employs three algorithms for respectively solving the three optimization modules to implement numerical simulations. The optimality and robustness of the computational guidance approach are verified with all constraints satisfied even in the presence of initial state uncertainty.

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“…After launch on December 8, 2018, CE-4 conducted several stages, including transfer from the Earth to the Moon, orbiting around the Moon and a powered descent. The powered descent stage was the most important stage for soft landing and was implemented under complete autonomous control 1 . According to the orbit design, a 7500 Newton variable propulsion engine was used for deceleration during the CE-4 powered descent stage, which involved phases of main braking, attitude adjusting, vertical descent, hover and hazard-avoidance, slow descent 1–5 .…”

Section: Introductionmentioning

confidence: 99%

Descent trajectory reconstruction and landing site positioning of Chang’E-4 on the lunar farside

et al. 2019

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Chang’E-4 (CE-4) was the first mission to accomplish the goal of a successful soft landing on the lunar farside. The landing trajectory and the location of the landing site can be effectively reconstructed and determined using series of images obtained during descent when there were no Earth-based radio tracking and the telemetry data. Here we reconstructed the powered descent trajectory of CE-4 using photogrammetrically processed images of the CE-4 landing camera, navigation camera, and terrain data of Chang’E-2. We confirmed that the precise location of the landing site is 177.5991°E, 45.4446°S with an elevation of −5935 m. The landing location was accurately identified with lunar imagery and terrain data with spatial resolutions of 7 m/p, 5 m/p, 1 m/p, 10 cm/p and 5 cm/p. These results will provide geodetic data for the study of lunar control points, high-precision lunar mapping, and subsequent lunar exploration, such as by the Yutu-2 rover.

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Guidance Summary and Assessment of the Chang’e-3 Powered Descent and Landing

Cited by 55 publications

References 10 publications

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Computational guidance for planetary powered descent using collaborative optimization

Descent trajectory reconstruction and landing site positioning of Chang’E-4 on the lunar farside

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